摘要
分析压气机稳定性的Ｅｕｌｅｒ模型张明川，唐狄毅关键词ＣＶＤ（化学气相沉积），预涂层，石墨粉，金刚石膜中图分类号ＴＢ４３旋转失速和喘振是压气机固有的不稳定工作现象，是一个具有挑战性的研究课题。以往的分析模型一般建立在小扰动理论基础上，适用于低速不可压流...
Rotating stall and surge are important aerodynamic unstable behavior in axial compressor. Many modeling approaches have been proposed in order to capture the essential physics of these complex flow phenomena. This paper presents a new non-linear model; CFD numerical approcach is used to simulate rotating stall and surge. It is an inviscld unsteady quaslthree dimensional model, and can simulate the flow instability in high speed multi-stage axial-flow compressors.The compressor or compression system is divided into blade-free and blade-row subelements. The overall now field includes different regions: 1. upstream inlet region; 2.blade rows; 3. axial gaps in compressor; 4. downstream region (including plenum and throttle). For regions 1, 3 and 4, the system of unsteady compressible Euler soverning equations is given as eq. (1).The blade row is modeled by a semi-disc model, i. e. an actuator disc and a localized volume. The blade row characteristics are expressed in terms of loss and turning-angle correlations, derived from quasi-steady-state approximation. First-order time lag equation is used to describe the blade's nonsteady response.The calculation begins with the steady circllmferential uniform background now field;then a two-dimensional small disturbance is superposed on this mean flow. Rotating stall and/or surge are/is stable, when the disturbance decays with time. Instability occurs when the disturbance increases with time.This model is a non-linear model for predicting rotating stall and surge in axial compressor. We calculate a single rotor compressor, a single stage compressol and a nine-stage compressor. The validity of this model is confirmed by comparison with test results.
出处
《西北工业大学学报》
EI
CAS
CSCD
北大核心
1996年第3期490-491,共2页
Journal of Northwestern Polytechnical University
基金
航空基金
关键词
压气机
稳定性
欧拉模型
旋转失速
rotating stall., surge, axial compressor, Eeler equation
